EP2758310A1 - Propulsion bay - Google Patents

Propulsion bay

Info

Publication number
EP2758310A1
EP2758310A1 EP12761734.8A EP12761734A EP2758310A1 EP 2758310 A1 EP2758310 A1 EP 2758310A1 EP 12761734 A EP12761734 A EP 12761734A EP 2758310 A1 EP2758310 A1 EP 2758310A1
Authority
EP
European Patent Office
Prior art keywords
bay
propulsion
power supply
space
temporarily
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP12761734.8A
Other languages
German (de)
French (fr)
Other versions
EP2758310B1 (en
Inventor
Pascal Bultel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Centre National dEtudes Spatiales CNES
Original Assignee
Centre National dEtudes Spatiales CNES
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Centre National dEtudes Spatiales CNES filed Critical Centre National dEtudes Spatiales CNES
Publication of EP2758310A1 publication Critical patent/EP2758310A1/en
Application granted granted Critical
Publication of EP2758310B1 publication Critical patent/EP2758310B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/421—Non-solar power generation
    • B64G1/422—Nuclear power generation
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/443—Photovoltaic cell arrays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/641—Interstage or payload connectors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B64G1/2427—Transfer orbits
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/405—Ion or plasma engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B64G1/411—Electric propulsion
    • B64G1/415—Arcjets or resistojets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/428—Power distribution and management
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
    • B64G1/503—Radiator panels

Definitions

  • the present invention relates to a propulsion bay intended to be transported, at least temporarily, in a space launcher, comprising an adapter for cooperation with at least one onboard system, at least temporarily, on the ba, the system comprising no power supply.
  • space launchers 2 are known for the transport, at least temporarily, of at least one space 16 on which equipment 6 or 7 and means 230 for propulsion are fixed.
  • Box 16 comprises an adapter 3, 4 for cooperation with at least the system 6 on board 16, at least temporarily.
  • the embedded system 6 generally forms an artificial satellite.
  • the launcher 2 For sending the system 6 into space and its m on orbit, the launcher 2 conventionally comprises several stages, namely:
  • a cryogenic lower stage 22 comprising a motor 220, with known liquid propulsion;
  • cryogenic upper stage 23 comprising a motor 230, with known liquid propulsion
  • a launch stage 24 having within it the system 6 protected by a cap 13.
  • stage 21 and 22 are first fired (E 1) for the launching of the launcher 2, and that then only the stage 22 is kept (E2) for the exit of the terrestrial atmosphere (stage 21 then separates from stage 22).
  • the cap 13 is then separated (E3) of the launcher 2 because it is heavy (typically 1, 7 tons) and now useless (at an altitude of about 69km, there is no atmosphere), then the floor 23 takes (E5) the relay of the propulsion after a step (E4) of separation from the stage 22.
  • the system 6 will then be separated from the box 16, once the motor 230 of the cut stage 23 (E6), and put into orbit.
  • the motor 230 of the stage 23 is a motor with liquid propulsion, and offers little flexibility of use (any interruption of its operation is indeed final). Because of the engine 230 with chemical fuels, the launcher payload 2 (that is to say the equipment intended to fulfill a specific mission (including the systems 6 and 7) and that carries the launcher 2 (and in particular the box 16)) is limited and can only be injected into one orbit.
  • the invention overcomes at least one of these disadvantages.
  • a propulsive bay intended to be transported, at least temporarily, in a space launcher, comprising: an adapter for cooperation with at least one onboard system, at least temporarily, on the bay, the system including a power supply.
  • the propulsive bay of the invention is characterized in that it further comprises at least one electric space propulsion motor adapted to be powered by the power supply of the system.
  • the adapter comprises a carrying structure comprising an internal space for receiving a first system embedded in the internal space;
  • the carrier structure has an end for cooperation with a second embedded system
  • the carrier structure comprises openings adapted for deployment of solar panels of the supply of a first artificial satellite system, through the openings;
  • the adapter is adapted for cooperation with a third embedded system forming an additional space, liquid or solid propulsion system.
  • the invention proposes a set comprising: a propulsive bay intended to be transported, at least temporarily, in a space launcher, comprising: a carrier structure comprising an internal space, at minus an electric space propulsion motor adapted to be powered by a power supply; and a first artificial satellite system embedded, at least temporarily, in the internal space of the carrier structure and having a power supply adapted to power the electric motor of the bay.
  • the power supply includes solar panels and the supporting structure has openings adapted for deployment of solar panels;
  • the power supply comprises a nuclear generator.
  • the bay comprises an onboard system forming an additional space, liquid or solid propulsion system.
  • the invention has many advantages.
  • the invention provides, with respect to the prior art known and presented in the introductory part of the present application, an additional propellant bay.
  • the invention makes it possible to provide a flexible propulsion of use, because it uses at least one electric propulsion engine spatial, low thrust but very powerful.
  • the invention allows a pooling of resources in the launcher, because it allows the use of the power supply of a system embedded on the bay for the power supply of the aforementioned electric motor of the bay: the mass gain on the bay can thus be transformed into an increase of the payload.
  • the invention thus makes it possible to increase the payload of the launcher, and in particular to increase the mass of the systems embedded on the bay, in particular the mass of the artificial satellites.
  • FIG. 3 and 4 show schematically views of a bay according to the invention, in perspective and partial transparency
  • FIGS. 5 and 6 show a top view and a bottom view of a bay according to FIGS. 3 and 4, respectively;
  • FIG. 7 schematically represents a possible embodiment of an electric space propulsion motor that can be used on a rack according to FIGS. 3 to 6;
  • FIG. 8 schematically shows a possible electrical installation for a power supply, by a system embedded on the bay, for an electric motor of the bay according to one of Figures 3 to 6;
  • FIG. 9 schematically show a side view of an adapter of a bay according to the invention.
  • FIG. 10 schematically shows a view of a detail of an adapter according to Figure 9, in perspective and partial transparency;
  • Figure 1 1 schematically shows an exploded view of a possible adapter of a bay according to the invention;
  • FIG. 12 schematically represents solar panels deployed from a power supply of embedded systems on a bay according to the invention
  • FIG. 13 schematically represents the possible options for an additional propulsion-based onboard system according to the invention.
  • FIG. 14 shows schematically an elastic cylinder separating a structure of the adapter bay with an upper part of the bay.
  • FIGS 3 to 14 schematically show a possible embodiment of a propulsive bay 1 according to the invention.
  • the bay 1 is intended to be housed in a launcher 2.
  • the bay 1 is additional and is housed in the launcher 2, at least temporarily, at a box 16. No adaptation of the launcher 2 is necessary for the bay housing 1.
  • the bay 1 therefore has dimensions adapted for its housing in the launcher 2: typically a diameter of a few meters and a height of the order of one meter.
  • the launcher 2 transporting the bay 1, at least temporarily is in accordance with the presentation made in the introductory part of the present application and its description is not repeated here for the sake of clarity and brevity.
  • the bay 1 has substantially a flattened cylindrical shape, and mainly comprises a peripheral belt 12 and equatorial, forming a torus having an internal space 127, and separating the bay 1 into two parts, namely a upper outer portion 121 and an outer lower portion 122.
  • the upper outer portion 121 is more clearly visible in FIG. 5, and the lower outer portion 122 is in turn visible in FIG.
  • the internal space 127 comprises in the lower peripheral part a ring 123, forming an equipment carrier, such as for example a housing 126 comprising, for example, an on-board computer controlling and controlling the bay 1.
  • an equipment carrier such as for example a housing 126 comprising, for example, an on-board computer controlling and controlling the bay 1.
  • the bay 1 thus also comprises an electric power supply 15, very advantageously formed by solar panels 15 of low power, for example 4 kilo watts, for powering the housing 126.
  • the panels 15 are for example two in number, and arranged in diametrically opposite one another relative to the periphery of the belt 12.
  • Bay 1 comprises liquid propulsion engines 125, for example monoergol, and tanks 124 for liquid fuel for engines 125.
  • the motors 125 are thus advantageously four in number, and arranged at equal distance from each other on the periphery of the bay 1, in order to obtain a redundancy of the motors 125 in the event of failure of one of the motors 125 and a cardan effect effective during attitude control.
  • the reservoirs 124 are advantageously in the form of spheres, and are carried by the ring 123 in the space 127.
  • the bay 1 also mainly comprises an adapter 3, 4, 5 for cooperation with at least 6, 7, or 8 onboard system.
  • the embedded system 6, 7, or 8 is on board at least temporarily on the bay 1.
  • the adapter 3, 5 is positioned at the upper portion 121.
  • Part 121 more precisely visible in FIGS. 3 and 5, comprises a structure 121 1 of substantially frustoconical shape at the periphery and flat at the central portion.
  • the structure 121 1 receives the adapter 3 at its center, the adapter 3 being of conical shape protruding from the structure 121 1, for a cooperation, by complementarity of shapes, with at least a lower part of a first embedded system 6, at least temporarily on bay 1.
  • the adapter 3, 5 also comprises a bearing structure 5 of substantially cylindrical shape and having an internal space 51 for receiving the first system 6 (see Figure 10).
  • the carrier structure also has an end 52 for cooperation with at least one second embedded system 7.
  • the end 52 is of conical shape projecting into the structure 5 for the cooperation, by complementarity of shapes, with a lower part of the second system 7 embedded.
  • the first system 6 forms an artificial satellite and / or the second system 7 forms an artificial satellite.
  • the first system 6 and / or the second system 7 comprises an electrical supply 9.
  • the bay 1 also comprises at least one electric space-propulsion motor 10, adapted to be powered by the power supply 9 of the system 6 or 7.
  • the motor 10 is powered exclusively by the electric supply 9 of the first system. 6 and / or the second system 7. It is therefore understood that there is a pooling of resources in the launcher, because of the use of the power supply of a system embedded on the bay for the power supply of the launcher. aforementioned electric motor of the bay: the mass gain on the bay can thus be transformed into an increase in the launcher payload, including an increase in the mass of embedded systems. As shown in FIG.
  • the power supply 9 of an on-board system is connected, by an electric power transfer link, to the electric motor 10 of the bay 1 via an electrical transformer T, either directly or via the intermediary of a battery B of the bay, for example placed in the box 126.
  • the transformer T can be placed on an embedded system, or can also be placed directly on the bay 1.
  • the electric space propulsion motor 10 is adapted to produce an electric / magnetic field and to be able to cause space propulsion by spatially expelling an electric / magnetic field responsive fuel.
  • the bay thus also comprises a reservoir 14 of fuel, for example of toric shape, and placed in the internal space 1 27 of the belt 12.
  • the fuel can thus be for example xenon, crypton, or argon.
  • the engine 10 may be of any type known to those skilled in the art, for example using
  • EIPT ponderomotive force propulsion
  • PPT pulsed plasma propulsion
  • - ionic propulsion such as a field ignition propellant (FEEP), a bombardment ion propellant, a radiofrequency ionization thruster or a Hall effect thruster (SPT, PPS, ALT)).
  • FEEP field ignition propellant
  • bombardment ion propellant such as a radiofrequency ionization thruster or a Hall effect thruster (SPT, PPS, ALT)
  • SPT Hall effect thruster
  • the propulsion of the electric motor 10 is relatively weak, but it is very flexible to use (on / off mode at will) and has a high efficiency.
  • the electric motor 10 is therefore advantageously used for phases requiring thrusts low but requiring high precision and high efficiency, for example but not limited to a final orbiting of an artificial satellite or for an orbit change of an artificial satellite.
  • the bay 1 comprises four motors 1 0 located equidistant from each other on the periphery of the bay 1 in order to obtain a redundancy of the motors 10 in case of failure of one of the motors and an effective gimbal effect during the attitude control of the bay 1 during the aforementioned phases.
  • the motors 10 are movable relative to the belt 12 between two positions, namely
  • the motor 10 comprises a support 102 of complementary shape to the belt 12, and also forming a radiator element, to allow the electric motor 10 to cool if necessary.
  • the adapter 4 is positioned at the lower portion 122.
  • the lower part 1 22 comprises a frustoconical peripheral device 1221 which is partially convex and a concave cone 1222 in the central part.
  • the structure 1221 and the cone 1222 allow recovery efforts.
  • the cone 1222 receives at its center the adapter 4, which is adapted for cooperation, by complementarity of shapes, with an on-board system, for example a third system 8 onboard advantageously forming additional liquid or solid space propulsion system.
  • a third system 8 onboard advantageously forming additional liquid or solid space propulsion system.
  • the third system 8 may be, of choice, of the type
  • the propulsion offered by the third system 8 can be used for a separation from the stage 23 and for flight phases requiring a strong propulsion.
  • the electric power supply 9 comprises solar panels 1 1 placed on the first system 6 and / or the second system 7, and transforming the solar radiation into electrical energy once deployed, in particular to the engine 10.
  • the solar panels 1 1 can produce a power of the order of 20 kW.
  • the carrier structure 5 has openings 53 adapted for deployment of the solar panels 1 1. of food 9.
  • the structure 5 comprises reinforcements 54 placed between a lower part of the supporting structure 5 and the upper structure 121 1.
  • the reinforcements 54 may thus be in the form of a structure made of a rigid lattice material, for example triangular, the base of which bears on the upper structure 121 1.
  • the electrical supply 9 comprises a transformer T (for example represented in FIG. 8) which is adapted to transform the mechanical energy of the liquid propulsion into electrical energy for the electric motor
  • the power supply 9 may comprise a nuclear generator instead of a thermal or solar generator, and may for example be located at the level of the systems 6 or 7.
  • the upper structure 2111 also comprises elastic cylinders 1214, known in themselves and mainly comprising a metal rod surrounded by a mechanical spring, held in elastic bias by pyrotechnic bolts 1213 and a peripheral strap 1215, also known in themselves.
  • the cylinders 1214 unfold and allow the mechanical separation of the structure 5 from the structure 121 1.
  • the bay 1 comprises four pairs of pyrotechnic bolts 1213 and six jacks 1214 of separation.
  • the bay 1 may also include other elements than those described, such as landing gear placed on the structure 1 221 low for certain types of m ission requiring landing of the bay 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Sustainable Development (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
  • High Energy & Nuclear Physics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Photovoltaic Devices (AREA)
  • Transmission Devices (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)
  • Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)

Abstract

The invention relates to a propulsion bay (1) intended to be transported, at least temporarily, in a space launch vehicle (2) and comprising an adapter (3) that co-operates with at least one system located, at least temporarily, on board the bay (1), said system comprising an electrical power supply. The bay is characterised in that it also comprises at least one electric space propulsion engine that can be powered by the power supply of the system.

Description

BAIE PROPULSIVE  PROPULSIVE BAY
DOMAINE TECHNIQUE GENERAL GENERAL TECHNICAL FIELD
La présente invention concerne une baie propulsive destinée à être transportée, au moins temporairement, dans un lanceur spatial, comportant un adaptateur pour une coopération avec au moins un système embarqué, au moins temporairement, su r la ba ie , le systèm e com portant u ne alimentation électrique. ETAT DE L'ART  The present invention relates to a propulsion bay intended to be transported, at least temporarily, in a space launcher, comprising an adapter for cooperation with at least one onboard system, at least temporarily, on the ba, the system comprising no power supply. STATE OF THE ART
Comme le montre la figure 1 , on connaît des lanceurs 2 spatiaux pour le transport, au moins temporaire, d'au moins une case 16 sur laquelle sont fixés des équipements 6 ou 7 et des moyens 230 de propulsion.  As shown in FIG. 1, space launchers 2 are known for the transport, at least temporarily, of at least one space 16 on which equipment 6 or 7 and means 230 for propulsion are fixed.
La case 16 comporte un adaptateur 3, 4 pour une coopération avec au moins le système 6 embarqué sur la case 16, au moins temporairement. Le système 6 embarqué forme en général un satellite artificiel.  Box 16 comprises an adapter 3, 4 for cooperation with at least the system 6 on board 16, at least temporarily. The embedded system 6 generally forms an artificial satellite.
Pour l'envoi du système 6 dans l'espace et sa m ise sur orbite, le lanceur 2 comporte classiquement plusieurs étages, à savoir :  For sending the system 6 into space and its m on orbit, the launcher 2 conventionally comprises several stages, namely:
- un étage 21 de décollage, comportant des propulseurs 210 d'appoint, à propulsion solide connue ;  - A takeoff stage 21, comprising thrusters 210 booster, known solid propulsion;
- un étage 22 inférieur cryogénique comportant un moteur 220, à propulsion liquide connue ;  a cryogenic lower stage 22 comprising a motor 220, with known liquid propulsion;
- un étage 23 supérieur cryogénique comportant un moteur 230, à propulsion liquide connue ; et  a cryogenic upper stage 23 comprising a motor 230, with known liquid propulsion; and
- un étage 24 de lancement comportant en son sein le système 6 protégé par une coiffe 13.  - A launch stage 24 having within it the system 6 protected by a cap 13.
On voit sur la figure 2 que les étages 21 et 22 sont d'abord mis à feu (E 1 ) pour le décollage du lanceur 2, et qu'ensuite seul l'étage 22 est conservé (E2) pour la sortie de l'atmosphère terrestre (l'étage 21 se sépare alors de l'étage 22). La coiffe 13 est ensuite séparé (E3) du lanceur 2 car il est lourd (typiquement 1 ,7 tonnes) et désormais inutile (à une altitude d'environ 69km, il n'y a plus d'atmosphère), puis l'étage 23 prend (E5) le relai de la propulsion après une étape (E4) de séparation d'avec l'étage 22. Le système 6 sera ensuite séparé de la case 16, une fois le moteur 230 de l'étage 23 coupé (E6), et mis sur orbite. It can be seen in FIG. 2 that the stages 21 and 22 are first fired (E 1) for the launching of the launcher 2, and that then only the stage 22 is kept (E2) for the exit of the terrestrial atmosphere (stage 21 then separates from stage 22). The cap 13 is then separated (E3) of the launcher 2 because it is heavy (typically 1, 7 tons) and now useless (at an altitude of about 69km, there is no atmosphere), then the floor 23 takes (E5) the relay of the propulsion after a step (E4) of separation from the stage 22. The system 6 will then be separated from the box 16, once the motor 230 of the cut stage 23 (E6), and put into orbit.
La tech n iq ue précéd ente con n ue présente ce pen dant d es inconvénients.  The previous tech nique has this disadvantage.
Le moteur 230 de l'étage 23 est un moteur à propulsion liquide, et offre peu de souplesse d'utilisation (toute coupure de son fonctionnement est en effet définitive). Du fait du moteur 230 à carburants chimiques, la charge utile du lanceur 2 (c'est-à-dire les équipements destinés à remplir une mission déterminée (notamment les systèmes 6 et 7) et que transporte le lanceur 2 (et notamment la case 16)) est limitée et ne peut être injectée que sur une seule orbite.  The motor 230 of the stage 23 is a motor with liquid propulsion, and offers little flexibility of use (any interruption of its operation is indeed final). Because of the engine 230 with chemical fuels, the launcher payload 2 (that is to say the equipment intended to fulfill a specific mission (including the systems 6 and 7) and that carries the launcher 2 (and in particular the box 16)) is limited and can only be injected into one orbit.
PRESENTATION DE L'INVENTION PRESENTATION OF THE INVENTION
L'invention permet de pallier au moins un de ces inconvénients.  The invention overcomes at least one of these disadvantages.
A cet effet, l'invention propose, selon un premier aspect, une baie propulsive destinée à être transportée, au moins temporairement, dans un lanceur spatial, comportant : un adaptateur pour une coopération avec au moins un système embarqué, au moins temporairement, sur la baie, le système comportant une alimentation électrique.  For this purpose, the invention proposes, according to a first aspect, a propulsive bay intended to be transported, at least temporarily, in a space launcher, comprising: an adapter for cooperation with at least one onboard system, at least temporarily, on the bay, the system including a power supply.
La baie propulsive de l' invention est caractérisée en ce qu'elle comporte en outre au moins un moteur électrique de propulsion spatiale adapté pour être alimenté par l'alimentation du système.  The propulsive bay of the invention is characterized in that it further comprises at least one electric space propulsion motor adapted to be powered by the power supply of the system.
L'invention selon le premier aspect est avantageusement complétée par les caractéristiques suivantes, prises seules ou en une quelconque de leur combinaison techniquement possible :  The invention according to the first aspect is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination:
- l'adaptateur comporte une structure porteuse comportant un espace interne pour la réception d'un premier système embarqué dans l'espace interne ;  the adapter comprises a carrying structure comprising an internal space for receiving a first system embedded in the internal space;
- la structure porteuse com porte u ne extrém ité pour u ne coopération avec un deuxième système embarqué ;  the carrier structure has an end for cooperation with a second embedded system;
- le prem ier système et/ou le deuxième système forment des satellites artificiels ; - la structure porteuse comporte des ouvertures adaptées pour un déploiement de panneaux solaires de l'alimentation d'un premier système formant satellite artificiel, par les ouvertures ;the first system and / or the second system form artificial satellites; - The carrier structure comprises openings adapted for deployment of solar panels of the supply of a first artificial satellite system, through the openings;
- l'adaptateur est adapté pour une coopération avec un troisième système embarqué formant système additionnel de propulsion spatiale, liquide ou solide. the adapter is adapted for cooperation with a third embedded system forming an additional space, liquid or solid propulsion system.
Et l' invention propose, selon un second aspect, un ensem ble caractérisé en ce qu'il comporte : une baie propulsive destinée à être transportée, au moins temporairement, dans un lanceur spatial, comportant : une structure porteuse comportant un espace interne, au moins un moteur électrique de propulsion spatiale adapté pour être alimenté par une alimentation électrique ; et un premier système formant satellite artificiel embarqué, au moins temporairement, dans l'espace interne de la structure porteuse et comportant une alimentation électrique adaptée pour alimenter le moteur électrique de la baie.  According to a second aspect, the invention proposes a set comprising: a propulsive bay intended to be transported, at least temporarily, in a space launcher, comprising: a carrier structure comprising an internal space, at minus an electric space propulsion motor adapted to be powered by a power supply; and a first artificial satellite system embedded, at least temporarily, in the internal space of the carrier structure and having a power supply adapted to power the electric motor of the bay.
L'invention selon le second aspect est avantageusement complétée par les caractéristiques suivantes, prises seules ou en une quelconque de leur combinaison techniquement possible :  The invention according to the second aspect is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination:
- l'alimentation électrique comporte des panneaux solaires et la structure porteuse comporte des ouvertures adaptées pour un déploiement des panneaux solaires ;  - The power supply includes solar panels and the supporting structure has openings adapted for deployment of solar panels;
- l'alimentation électrique comporte un générateur nucléaire. the power supply comprises a nuclear generator.
- la baie comporte un système embarqué formant système additionnel de propulsion spatiale, liquide ou solide. L'invention présente de nombreux avantages. the bay comprises an onboard system forming an additional space, liquid or solid propulsion system. The invention has many advantages.
L'invention prévoit, par rapport à l'art antérieur connu et présenté dans la partie introductive de la présente demande, une baie propulsive additionnelle.  The invention provides, with respect to the prior art known and presented in the introductory part of the present application, an additional propellant bay.
L'invention permet de prévoir une propulsion souple d'utilisation, car elle utilise au moins un moteur électrique de propulsion spatiale, de poussée faible mais très performante.  The invention makes it possible to provide a flexible propulsion of use, because it uses at least one electric propulsion engine spatial, low thrust but very powerful.
L'invention permet une mutualisation des ressources dans le lanceur, car elle permet l'utilisation de l'alimentation électrique d'un système embarqué sur la baie pour l'alimentation électrique du moteur électrique précité de la baie : le gain de masse sur la baie peut ainsi être transformé en une augmentation de la charge utile. The invention allows a pooling of resources in the launcher, because it allows the use of the power supply of a system embedded on the bay for the power supply of the aforementioned electric motor of the bay: the mass gain on the bay can thus be transformed into an increase of the payload.
L'invention permet ainsi d'augmenter la charge utile du lanceur, et notamment d'augmenter la masse des systèmes embarqués sur la baie, notamment la masse des satellites artificiels.  The invention thus makes it possible to increase the payload of the launcher, and in particular to increase the mass of the systems embedded on the bay, in particular the mass of the artificial satellites.
PRESENTATION DES FIGURES PRESENTATION OF FIGURES
D' autres caractéristiques, buts et avantages de l' invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard des dessins annexés sur lesquels :  Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings in which:
- les figures 1 et 2, déjà commentées, représentent schématiquement respectivement un lanceur connu et son mode de lancement ;  - Figures 1 and 2, already commented, schematically respectively show a known launcher and its launch mode;
- les figures 3 et 4 représentent schématiquement des vues d'une baie selon l'invention, en perspective et en transparence partielle ;  - Figures 3 and 4 show schematically views of a bay according to the invention, in perspective and partial transparency;
- l e s f i g u re s 5 et 6 re p ré s e n t e n t s c h é m at i q u e m e n t respectivement une vue supérieure et une vue inférieure d'une baie selon les figures 3 et 4 ;  FIGS. 5 and 6 show a top view and a bottom view of a bay according to FIGS. 3 and 4, respectively;
- la figure 7 représente schématiquement un mode de réalisation possible d'un moteur électrique de propulsion spatiale, pouvant être utilisé sur une baie selon les figures 3 à 6 ;  FIG. 7 schematically represents a possible embodiment of an electric space propulsion motor that can be used on a rack according to FIGS. 3 to 6;
- la figure 8 représente schématiquement un montage électrique possible pour une alimentation électrique, par un système embarqué sur la baie, pour un moteur électrique de la baie selon l'une des figures 3 à 6 ;  - Figure 8 schematically shows a possible electrical installation for a power supply, by a system embedded on the bay, for an electric motor of the bay according to one of Figures 3 to 6;
- la figure 9 représentent schématiquement une vue de côté d'un adaptateur d'une baie selon l'invention ;  - Figure 9 schematically show a side view of an adapter of a bay according to the invention;
- la figure 10 représente schématiquement une vue d'un détail d'un adaptateur selon la figure 9, en perspective et en transparence partielle ; - la figure 1 1 représente schématiquement une vue éclatée d'un adaptateur possible d'une baie selon l'invention ; - Figure 10 schematically shows a view of a detail of an adapter according to Figure 9, in perspective and partial transparency; - Figure 1 1 schematically shows an exploded view of a possible adapter of a bay according to the invention;
- la figure 12 représente schématiquement des panneaux solaires déployés d'une alimentation de systèmes embarqués sur une baie selon l'invention ;  FIG. 12 schematically represents solar panels deployed from a power supply of embedded systems on a bay according to the invention;
- la figure 13 représente schématiquement les options possibles pour un système embarqué formant propulsion additionnelle de la baie selon l'invention ; et  FIG. 13 schematically represents the possible options for an additional propulsion-based onboard system according to the invention; and
- la figure 14 représente schématiquement un vérin élastique de séparation d'une structure de l'adaptateur de la baie d'avec une partie supérieure de la baie.  - Figure 14 shows schematically an elastic cylinder separating a structure of the adapter bay with an upper part of the bay.
S u r l'ensemble des figures, les éléments sim ilaires portent des références numériques identiques. DESCRIPTION DETAILLEE  For all the figures, the sim ilar elements bear identical numerical references. DETAILED DESCRIPTION
Les fig ures 3 à 14 représentent schématiquement un mode de réalisation possible d'une baie 1 propulsive selon l'invention.  Figures 3 to 14 schematically show a possible embodiment of a propulsive bay 1 according to the invention.
La baie 1 est destinée à être logée dans un lanceur 2.  The bay 1 is intended to be housed in a launcher 2.
Par rapport au lanceur 2 présenté en référence à l'art antérieur, la baie 1 est additionnelle et est logée dans le lanceur 2, au moins temporairement, au niveau d'une case 16. Aucune adaptation du lanceur 2 n'est nécessaire pour le logement de la baie 1. La baie 1 présente donc des dimensions adaptées pour son logement dans le lanceur 2 : typiquement un diamètre de quelques mètres et une hauteur de l'ordre du mètre. Hormis cette différence, le lanceur 2 transportant la baie 1 , au moins temporairement, est conforme à la présentation faite dans la partie introductive de la présente demande et sa description n'est pas reprise ici pour des raisons de clarté et de concision.  Compared to the launcher 2 presented with reference to the prior art, the bay 1 is additional and is housed in the launcher 2, at least temporarily, at a box 16. No adaptation of the launcher 2 is necessary for the bay housing 1. The bay 1 therefore has dimensions adapted for its housing in the launcher 2: typically a diameter of a few meters and a height of the order of one meter. Apart from this difference, the launcher 2 transporting the bay 1, at least temporarily, is in accordance with the presentation made in the introductory part of the present application and its description is not repeated here for the sake of clarity and brevity.
Comme le montrent les figures 3 et 4, la baie 1 présente sensiblement une forme cylindrique aplatie, et comporte principalement une ceinture 12 périphérique et équatoriale, formant un tore comportant un espace 127 interne, et séparant la baie 1 en deux parties, à savoir une partie 121 externe supérieure et une partie 122 externe inférieure. La partie 121 externe supérieure est plus précisément visible à la figure 5, et la partie 122 externe inférieure est quant à elle visible à la figure 6. As shown in Figures 3 and 4, the bay 1 has substantially a flattened cylindrical shape, and mainly comprises a peripheral belt 12 and equatorial, forming a torus having an internal space 127, and separating the bay 1 into two parts, namely a upper outer portion 121 and an outer lower portion 122. The upper outer portion 121 is more clearly visible in FIG. 5, and the lower outer portion 122 is in turn visible in FIG.
L'espace 127 interne comporte en partie basse périphérique un anneau 123, formant plateau porte-équipement, comme par exemple un boîtier 126 comportant par exemple un ordinateur de bord de commande et de pilotage de la baie 1 .  The internal space 127 comprises in the lower peripheral part a ring 123, forming an equipment carrier, such as for example a housing 126 comprising, for example, an on-board computer controlling and controlling the bay 1.
La baie 1 comporte ainsi également une alimentation 15 électrique, très avantageusement formée par des panneaux solaires 15 de faible puissance, par exemple 4 KiloWatts, pour l'alimentation du boîtier 126. Les panneaux 15 sont par exemple au nombre de deux, et disposés de manière diamétralement opposés l'un par rapport à l'autre sur la périphérie de la ceinture 12.  The bay 1 thus also comprises an electric power supply 15, very advantageously formed by solar panels 15 of low power, for example 4 kilo watts, for powering the housing 126. The panels 15 are for example two in number, and arranged in diametrically opposite one another relative to the periphery of the belt 12.
La baie 1 comporte des moteurs 125 de propulsion liquide, par exemple monoergol, et des réservoirs 124 de carburant liquide pour les moteurs 125.  Bay 1 comprises liquid propulsion engines 125, for example monoergol, and tanks 124 for liquid fuel for engines 125.
Les moteurs 125 permettent de fournir  125 engines can provide
- une propulsion supplémentaire nécessaire à la séparation de la baie 1 d'avec l'étage 23, ainsi que  an additional propulsion necessary for the separation of the bay 1 from the stage 23, as well as
- un contrôle d'attitude de la baie 1 lors de son pilotage après la séparation précitée.  an attitude control of the bay 1 during its piloting after the aforementioned separation.
Les moteurs 125 sont ainsi avantageusement au nombre de quatre, et disposés à égale distance les uns des autres sur la périphérie de la baie 1 , afin d'obtenir une redondance des moteurs 125 en cas de panne de l'un des moteurs 125 et un effet cardan efficace lors du contrôle d'attitude.  The motors 125 are thus advantageously four in number, and arranged at equal distance from each other on the periphery of the bay 1, in order to obtain a redundancy of the motors 125 in the event of failure of one of the motors 125 and a cardan effect effective during attitude control.
Les réservoirs 124 sont avantageusement en forme de sphères, et sont portés par l'anneau 123 dans l'espace 127.  The reservoirs 124 are advantageously in the form of spheres, and are carried by the ring 123 in the space 127.
La baie 1 comporte également principalement un adaptateur 3, 4, 5 pour une coopération avec au moins système embarqué 6, 7, ou 8. Le système embarqué 6, 7, ou 8 est embarqué au moins temporairement sur la baie 1 .  The bay 1 also mainly comprises an adapter 3, 4, 5 for cooperation with at least 6, 7, or 8 onboard system. The embedded system 6, 7, or 8 is on board at least temporarily on the bay 1.
Selon un mode de réalisation préférentiel, l'adaptateur 3, 5 est positionné au niveau de la partie 121 supérieure. La partie 121 , plus précisément visible sur les figures 3 et 5, comporte une structure 121 1 supérieure de forme sensiblement tronconique en périphérie et plate en partie centrale. According to a preferred embodiment, the adapter 3, 5 is positioned at the upper portion 121. Part 121, more precisely visible in FIGS. 3 and 5, comprises a structure 121 1 of substantially frustoconical shape at the periphery and flat at the central portion.
La structure 121 1 reçoit l'adaptateur 3 en son centre, l'adaptateur 3 étant de forme conique en saillie par rapport à la structure 121 1 , pour une coopération, par complémentarité de formes, avec au moins une partie inférieure d'un premier système 6 embarqué, au moins temporairement sur la baie 1 .  The structure 121 1 receives the adapter 3 at its center, the adapter 3 being of conical shape protruding from the structure 121 1, for a cooperation, by complementarity of shapes, with at least a lower part of a first embedded system 6, at least temporarily on bay 1.
Comme le montrent les figures 9 à 1 1 , l'adaptateur 3, 5 comporte également une structure 5 porteuse de forme sensiblement cylindrique et comportant un espace interne 51 pour la réception du premier système 6 (voir figure 10).  As shown in Figures 9 to 1 1, the adapter 3, 5 also comprises a bearing structure 5 of substantially cylindrical shape and having an internal space 51 for receiving the first system 6 (see Figure 10).
La structure 5 porteuse comporte également une extrémité 52 pour une coopération avec au moins un deuxième système 7 embarqué.  The carrier structure also has an end 52 for cooperation with at least one second embedded system 7.
De même que pour la partie de l'adaptateur 3, 5 située au niveau de la structure 121 1 , l'extrémité 52 est de forme conique formant saillie dans la structure 5 pour la coopération, par complémentarité de formes, avec une partie inférieure du deuxième système 7 embarqué.  As for the part of the adapter 3, 5 situated at the level of the structure 121 1, the end 52 is of conical shape projecting into the structure 5 for the cooperation, by complementarity of shapes, with a lower part of the second system 7 embedded.
De manière tout à fait classique, le prem ier système 6 forme un satellite artificiel et/ou le deuxième système 7 forme un satellite artificiel. A cet égard, le premier système 6 et/ou le deuxième système 7 comportent une alimentation 9 électrique.  In a quite conventional manner, the first system 6 forms an artificial satellite and / or the second system 7 forms an artificial satellite. In this regard, the first system 6 and / or the second system 7 comprises an electrical supply 9.
La baie 1 comporte également au moins un moteur 10 électrique de propulsion spatiale, adapté pour être alimenté par l'alimentation 9 du système 6 ou 7. De manière très avantageuse, le moteur 10 est alimenté exclusivement par l'alimentation 9 électrique du premier système 6 et/ou du deuxième système 7. On comprend donc qu'il y a une mutualisation des ressources dans le lanceur, du fait de l'utilisation de l'alimentation électrique d'un système embarqué sur la baie pour l'alimentation électrique du moteur électrique précité de la baie : le gain de masse sur la baie peut ainsi être transformé en une augmentation de la charge utile du lanceur, notamment une augmentation de la masse des systèmes embarqués. Comme le montre la figure 8, l'alimentation électrique 9 d'un système embarqué est reliée, par un lien électrique de transfert de puissance électrique, au moteur 10 électrique de la baie 1 via un transformateur T électrique, soit directement, soit par l'intermédiaire d'une batterie B de la baie, par exemple placée dans la case 126. Le transformateur T peut être placé sur un système embarqué, ou peut également être placé directement sur la baie 1 . The bay 1 also comprises at least one electric space-propulsion motor 10, adapted to be powered by the power supply 9 of the system 6 or 7. In a very advantageous manner, the motor 10 is powered exclusively by the electric supply 9 of the first system. 6 and / or the second system 7. It is therefore understood that there is a pooling of resources in the launcher, because of the use of the power supply of a system embedded on the bay for the power supply of the launcher. aforementioned electric motor of the bay: the mass gain on the bay can thus be transformed into an increase in the launcher payload, including an increase in the mass of embedded systems. As shown in FIG. 8, the power supply 9 of an on-board system is connected, by an electric power transfer link, to the electric motor 10 of the bay 1 via an electrical transformer T, either directly or via the intermediary of a battery B of the bay, for example placed in the box 126. The transformer T can be placed on an embedded system, or can also be placed directly on the bay 1.
Comme le montre la figure 7, le moteur 1 0 électrique de propulsion spatiale est adapté pour produire un champ électrique/magnétique et pour pouvoir provoquer une propulsion spatiale en expulsant dans l'espace un carburant sensible au champ électrique/magnétique.  As shown in FIG. 7, the electric space propulsion motor 10 is adapted to produce an electric / magnetic field and to be able to cause space propulsion by spatially expelling an electric / magnetic field responsive fuel.
La baie comporte donc également un réservoir 14 de carburant, par exemple de forme torique, et placée dans l'espace 1 27 interne de la ceinture 12. Le carburant peut être ainsi par exemple du xénon, du crypton, ou de l'argon.  The bay thus also comprises a reservoir 14 of fuel, for example of toric shape, and placed in the internal space 1 27 of the belt 12. The fuel can thus be for example xenon, crypton, or argon.
Le moteur 10 peut être de tout type connu par l'homme du métier, par exemple utiliser  The engine 10 may be of any type known to those skilled in the art, for example using
- la propulsion électrothermique, et/ou  - electrothermal propulsion, and / or
- la propulsion électromagnétique (propulseur du type magnétoplasma dynamique (MPD) ou accélérateur utilisant les forces de Lorentz - electromagnetic propulsion (Dynamic Magnetoplasma type propulsion (MPD) or accelerator using Lorentz forces
(LFA ou Lorentz force accelerator)), et/ou (LFA or Lorentz force accelerator)), and / or
- la propulsion à force pondéromotrice (EIPT), et/ou  - ponderomotive force propulsion (EIPT), and / or
- la propulsion à plasma puisé (PPT), et/ou  - pulsed plasma propulsion (PPT), and / or
- la propulsion ionique (comme par exemple un propulseur à ignition de champs (FEEP), un propulseur ionique à bombardement, un propulseur à ionisation à radiofréquence ou un propulseur à effet Hall (SPT, PPS, ALT)).  - ionic propulsion (such as a field ignition propellant (FEEP), a bombardment ion propellant, a radiofrequency ionization thruster or a Hall effect thruster (SPT, PPS, ALT)).
Contrairement à la propulsion liquide offerte par les moteurs 125, qui est utilisée pour une séparation d'avec l'étage 23 et pour des phases de vol requérant une forte propulsion, la propulsion du moteur électrique 10 est relativement peu puissante, mais elle est très souple d'utilisation (mode marche/arrêt à volonté) et a un haut rendement. Le moteur électrique 10 est donc avantageusement utilisé pour des phases nécessitant des poussées faibles mais requérant une haute précision et un haut rendement, par exemple mais non limitativement pour une mise sur orbite définitive d'un satellite artificiel ou pour un changement d'orbite d'un satellite artificiel. Unlike the liquid propulsion offered by the motors 125, which is used for a separation from the stage 23 and for flight phases requiring a strong propulsion, the propulsion of the electric motor 10 is relatively weak, but it is very flexible to use (on / off mode at will) and has a high efficiency. The electric motor 10 is therefore advantageously used for phases requiring thrusts low but requiring high precision and high efficiency, for example but not limited to a final orbiting of an artificial satellite or for an orbit change of an artificial satellite.
De même que précédemment pour les moteurs 125, préférentiellement, la baie 1 comporte quatre moteurs 1 0 situés à égale distance l'un de l'autre sur la périphérie de la baie 1 afin d'obtenir une redondance des moteurs 10 en cas de panne de l'un des moteurs et un effet cardan efficace lors du contrôle d'attitude de la baie 1 lors des phases précitées.  As previously for the motors 125, preferably, the bay 1 comprises four motors 1 0 located equidistant from each other on the periphery of the bay 1 in order to obtain a redundancy of the motors 10 in case of failure of one of the motors and an effective gimbal effect during the attitude control of the bay 1 during the aforementioned phases.
Comme le montrent les doubles flèches de la figure 4, les moteurs 10 sont mobiles par rapport à la ceinture 12 entre deux positions, à savoir  As shown by the double arrows in FIG. 4, the motors 10 are movable relative to the belt 12 between two positions, namely
- une position escamotée dans laquelle le moteur 10 est plaqué contre la ceinture 12, pour permettre le positionnement de la baie 1 dans le lanceur 2 (la position escamotée des moteurs 10 est par exemple visible sur les figures 9 et 10), et  - A retracted position in which the motor 10 is pressed against the belt 12, to allow the positioning of the bay 1 in the launcher 2 (the retracted position of the motors 10 is for example visible in Figures 9 and 10), and
- une position déployée permettant la propu lsion de la baie si nécessaire, visible sur les figures 3, 4, 5 et 6 notamment.  - An extended position allowing the propu lsion of the bay if necessary, visible in Figures 3, 4, 5 and 6 in particular.
Comme on peut le constater sur les figures 3 et 4, le moteur 1 0 comporte un support 102, de forme complémentaire à la ceinture 12, et formant également élément radiateur, pour permettre le refroidissement du moteur électrique 10 si nécessaire.  As can be seen in FIGS. 3 and 4, the motor 10 comprises a support 102 of complementary shape to the belt 12, and also forming a radiator element, to allow the electric motor 10 to cool if necessary.
Comme le montrent la figure 4 et la figure 6, selon un mode de réalisation préférentiel, alternatif au mode de réalisation décrit ci-dessus, ou en complément de ce dernier, l'adaptateur 4 est positionné au niveau de la partie 122 inférieure.  As shown in Figure 4 and Figure 6, according to a preferred embodiment, alternative to the embodiment described above, or in addition to the latter, the adapter 4 is positioned at the lower portion 122.
La partie i nférieure 1 22 com porte une structure 1221 basse périphérique tronconique, partiellement convexe, et un cône 1222 concave en partie centrale. La structure 1221 et le cône 1222 permettent une reprise des efforts.  The lower part 1 22 comprises a frustoconical peripheral device 1221 which is partially convex and a concave cone 1222 in the central part. The structure 1221 and the cone 1222 allow recovery efforts.
Le cône 1222 reçoit en son centre l'adaptateur 4, qui est adapté pour une coopération, par complémentarité de formes, avec système embarqué, par exemple un troisième système 8 embarqué formant avantageusement système additionnel de propulsion spatiale liquide ou solide. Comme le montre la figure 13, le troisième système 8 peut être, au choix, de type The cone 1222 receives at its center the adapter 4, which is adapted for cooperation, by complementarity of shapes, with an on-board system, for example a third system 8 onboard advantageously forming additional liquid or solid space propulsion system. As shown in FIG. 13, the third system 8 may be, of choice, of the type
- propulsion 8a solide connue, ou  known solid propulsion 8a, or
- propulsion 8b liquide connue, ou  - known liquid 8b propulsion, or
ostockable  ostockable
ocryogénique  ocryogénique
- propulsion 8c hybride connue, avec réservoir 141 supplémentaire de carburant pour le moteur 10, ou  - Known 8c hybrid propulsion, with additional fuel tank 141 for engine 10, or
De même que la propulsion liquide offerte par les moteurs 125, la propulsion offerte par le troisième système 8 peut être utilisée pour une séparation d'avec l'étage 23 et pour des phases de vol requérant une forte propulsion.  As well as the liquid propulsion offered by the motors 125, the propulsion offered by the third system 8 can be used for a separation from the stage 23 and for flight phases requiring a strong propulsion.
Comme le montre la figure 12, dans le cas tout à fait classique où le premier système 6 forme un satellite artificiel et/ou le deuxième système 7 forme un satellite artificiel, l'alimentation 9 électrique comporte des panneaux 1 1 solaires, placés sur le premier système 6 et/ou sur le deuxième système 7, et transformant le rayonnement solaire en énergie électrique une fois déployés, notamment à destination du moteur 10. Les panneaux 1 1 solaires peuvent produire une puissance de l'ordre de 20 kW.  As is shown in FIG. 12, in the quite conventional case where the first system 6 forms an artificial satellite and / or the second system 7 forms an artificial satellite, the electric power supply 9 comprises solar panels 1 1 placed on the first system 6 and / or the second system 7, and transforming the solar radiation into electrical energy once deployed, in particular to the engine 10. The solar panels 1 1 can produce a power of the order of 20 kW.
Comme on peut le constater sur la figure 12, afin de pouvoir déployer les panneaux 1 1 solaires du système 6 encore en place sur l'adaptateur 3, 5, la structure porteuse 5 comporte des ouvertures 53 adaptées pour un déploiement des panneaux 1 1 solaires de l'alimentation 9.  As can be seen in FIG. 12, in order to be able to deploy the solar panels 1 1 of the system 6 still in place on the adapter 3, 5, the carrier structure 5 has openings 53 adapted for deployment of the solar panels 1 1. of food 9.
Afin de garder la rigidité de la structure porteuse 5, malgré la présence des ouvertures 53, la structure 5 comporte des renforts 54 placés entre une partie inférieure de la structure porteuse 5 et la structure 121 1 supérieure.  In order to maintain the rigidity of the supporting structure 5, despite the presence of the openings 53, the structure 5 comprises reinforcements 54 placed between a lower part of the supporting structure 5 and the upper structure 121 1.
Les renforts 54 peuvent être ainsi sous la forme d'une structure en matériau rigide en treillis, par exemple triangulaire, dont la base prend appui sur la structure supérieure 121 1 .  The reinforcements 54 may thus be in the form of a structure made of a rigid lattice material, for example triangular, the base of which bears on the upper structure 121 1.
De manière avantageuse, dans le cas tout à fait classique où le troisième système 8 forme un système additionnel de propulsion spatiale liquide ou solide, l'alimentation 9 électrique comporte un transformateur T (par exemple représenté sur la figure 8) qui est adapté pour transformer l'énergie mécanique de la propulsion liquide en énergie électrique pour le moteur 10 électrique Advantageously, in the quite conventional case where the third system 8 forms an additional system of liquid or solid spatial propulsion, the electrical supply 9 comprises a transformer T (for example represented in FIG. 8) which is adapted to transform the mechanical energy of the liquid propulsion into electrical energy for the electric motor
Selon une variante, l'alimentation 9 peut comporter un générateur nucléaire au lieu d'un générateur thermique ou solaire, et être par exemple situé au niveau des systèmes 6 ou 7.  According to one variant, the power supply 9 may comprise a nuclear generator instead of a thermal or solar generator, and may for example be located at the level of the systems 6 or 7.
De manière classique, la structure 1 21 1 supérieure com porte également des vérins élastiques 1214, connus en eux-mêmes et comportant principalement une tige métal l ique entourée d'un ressort mécanique, maintenus en sollicitation élastique grâce à des bou lons pyrotechniques 1213 et une sangle 1215 périphérique, également connus en eux-mêmes. Au moment de l'explosion des boulons pyrotechniques et de la sangle 1215, les vérins 1214 se déploient et permettent la séparation mécanique de la structure 5 d'avec la structure 121 1. Avantageusement, la baie 1 comporte quatre paires de boulons 1213 pyrotechniques et six vérins 1214 de séparation.  Conventionally, the upper structure 2111 also comprises elastic cylinders 1214, known in themselves and mainly comprising a metal rod surrounded by a mechanical spring, held in elastic bias by pyrotechnic bolts 1213 and a peripheral strap 1215, also known in themselves. At the time of the explosion of the pyrotechnic bolts and the strap 1215, the cylinders 1214 unfold and allow the mechanical separation of the structure 5 from the structure 121 1. Advantageously, the bay 1 comprises four pairs of pyrotechnic bolts 1213 and six jacks 1214 of separation.
On comprend que la baie 1 peut comporter également d'autres éléments que ceux décrits, comme par exemple des trains d'atterrissage placés sur la structure 1 221 basse, pour certains types de m ission requérant un atterrissage de la baie 1 .  It is understood that the bay 1 may also include other elements than those described, such as landing gear placed on the structure 1 221 low for certain types of m ission requiring landing of the bay 1.

Claims

REVENDICATIONS
1 . Baie (1 ) propulsive destinée à être transportée, au m o i ns temporairement, dans un lanceur (2) spatial, comportant : 1. Propulsive bay (1) intended to be transported temporarily to a space launcher (2) comprising:
- un adaptateur (3, 4, 5) pour une coopération avec au moins un système embarqué (6, 7, 8), temporairement, sur la baie (1 ), l'adaptateur comportant une structure (5) porteuse comportant un espace interne (51 ) pour la réception d'un premier système (6) embarqué dans l'espace interne (51 ), la structure (5) porteuse comportant une extrémité (52) pour une coopération avec un deuxième système (7) embarqué, l'adaptateur (4) étant adapté pour une coopération avec un troisième système (8) embarqué formant système additionnel de propulsion spatiale, liquide ou solide, le système (6, 7, 8) comportant une alimentation (9) électrique, an adapter (3, 4, 5) for cooperation with at least one onboard system (6, 7, 8) temporarily on the bay (1), the adapter comprising a structure (5) carrying a carrier having an internal space (51) for receiving a first system (6) embedded in the internal space (51), the carrier structure (5) having an end (52) for cooperation with a second system (7) on board, the adapter (4) being adapted for cooperation with a third onboard system (8) forming an additional space, liquid or solid propulsion system, the system (6, 7, 8) comprising an electric power supply (9),
- au moins un moteur (10) électrique de propulsion spatiale adapté pour être alimenté par l'alimentation (9) du système (6, 7, 8).  - At least one electric motor (10) for spatial propulsion adapted to be powered by the power supply (9) of the system (6, 7, 8).
2. Baie selon la revendication 1 , dans laquelle le premier système (6) et/ou le deuxième système (7) forment des satellites artificiels. 2. Bay according to claim 1, wherein the first system (6) and / or the second system (7) form artificial satellites.
3. Baie selon la revendication précédente, dans laquelle la structure porteuse (5) comporte des ouvertures (53) adaptées pour un déploiement de panneaux solaires (1 1 ) de l'alimentation (9) d'un premier système (6) formant satellite artificiel, par les ouvertures (53). 3. Bay according to the preceding claim, wherein the carrier structure (5) comprises openings (53) adapted for deployment of solar panels (1 1) of the power supply (9) of a first system (6) forming a satellite artificial, through the openings (53).
4. Ensemble caractérisé en ce qu'il comporte : 4. characterized in that it comprises:
- une baie ( 1 ) propu lsive desti née à être transportée, au m oins temporairement, dans un lanceur (2) spatial, comportant :  - a propulsive bay (1) desti ned to be transported, at least temporarily, in a launcher (2) space, comprising:
- une structure (5) porteuse comportant un espace interne (51 ), a carrier structure (5) comprising an internal space (51),
- au moins un moteur (10) électrique de propulsion spatiale alimenté par une alimentation (9) électrique ; et at least one electric space propulsion motor (10) powered by an electric power supply (9); and
- u n prem ier systèm e (6) form ant satel l ite artificie l em barq ué , temporairement, dans l'espace interne (51 ) de la structure (5) porteuse et comportant une alimentation (9) électrique alimentant le moteur ( 1 0) électrique de la baie (1 ). a first system (6) for forming the artifact emitted temporarily in the internal space (51) of the carrier structure (5) and having an electric power supply (9) supplying the electric motor (1 0) of the bay (1).
5. Ensemble selon la revendication 4, dans lequel l'alimentation (9) électrique comporte des panneaux solaires et la structure porteuse (5) comporte des ouvertures (53) adaptées pour un déploiement des panneaux solaires (1 1 ). 5. The assembly of claim 4, wherein the power supply (9) comprises solar panels and the carrier structure (5) has openings (53) adapted for deployment of the solar panels (1 1).
6. Ensemble selon la revendication 4, dans lequel l'alimentation (9) électrique comporte un générateur nucléaire. 6. The assembly of claim 4, wherein the power supply (9) comprises a nuclear generator.
7. Ensemble, selon l'une des revendications 4 à 6, dans lequel la baie (1 ) comporte un système (8) embarqué formant système additionnel de propulsion spatiale, liquide ou solide. 7. The assembly according to one of claims 4 to 6, wherein the bay (1) comprises an onboard system (8) forming additional space propulsion system, liquid or solid.
EP12761734.8A 2011-09-20 2012-09-20 Propulsion bay Active EP2758310B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1158366A FR2980177B1 (en) 2011-09-20 2011-09-20 PROPULSIVE BAY
PCT/EP2012/068490 WO2013041598A1 (en) 2011-09-20 2012-09-20 Propulsion bay

Publications (2)

Publication Number Publication Date
EP2758310A1 true EP2758310A1 (en) 2014-07-30
EP2758310B1 EP2758310B1 (en) 2019-01-16

Family

ID=46881062

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12761734.8A Active EP2758310B1 (en) 2011-09-20 2012-09-20 Propulsion bay

Country Status (9)

Country Link
US (1) US9963250B2 (en)
EP (1) EP2758310B1 (en)
JP (1) JP2014530144A (en)
CN (1) CN103930348B (en)
CA (1) CA2849338C (en)
FR (1) FR2980177B1 (en)
IL (1) IL231640A (en)
RU (1) RU2566511C1 (en)
WO (1) WO2013041598A1 (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3002594B1 (en) 2013-02-26 2016-09-30 Snecma SPIRAL PROPULSION MODULE WITH ELECTRIC PROPULSION AND CHEMICAL WITH SOLID PROPERGOL
US9712031B2 (en) * 2013-07-17 2017-07-18 Harold Ellis Ensle Electromagnetic propulsion system
US20150083865A1 (en) * 2013-09-23 2015-03-26 The Boeing Company Multiple spacecraft launch system
CN103786902B (en) * 2013-12-24 2016-03-02 兰州空间技术物理研究所 Spacecraft electric thruster more changer adapter in-orbit
CN104260901B (en) * 2014-09-11 2016-08-24 上海卫星工程研究所 Modular bipropellant propulsion system
CN104260903B (en) * 2014-09-16 2016-05-11 上海卫星工程研究所 Possesses the propelling module structure of independent high rail satellite platform function
US20170210494A1 (en) * 2016-01-21 2017-07-27 The Boeing Company Unpressurized cargo transfer pallet and structural support
US10913551B1 (en) * 2018-02-14 2021-02-09 Lockheed Martin Corporation Fault-tolerant scalable high thrust spacecraft propulsion
FR3078952B1 (en) * 2018-03-16 2020-03-27 Arianegroup Sas WORKING ORBIT SYSTEM FOR A SATELLITE
US11560243B2 (en) 2019-02-22 2023-01-24 Blue Origin, Llc Spacecraft multifunction connecting mechanisms including interchangeable port opening docking mechanisms, and associated systems and methods
US11565628B2 (en) * 2019-03-29 2023-01-31 Blue Origin, Llc Spacecraft with increased cargo capacities, and associated systems and methods
CN110562496B (en) * 2019-08-21 2021-05-11 上海航天控制技术研究所 Integrated satellite propulsion system
CN112344807B (en) * 2020-10-27 2022-08-09 中国运载火箭技术研究院 Carrier rocket
US11987395B2 (en) 2021-06-07 2024-05-21 Blue Origin, Llc Thrusting rails for launch vehicles, and associated systems and methods

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5350137A (en) * 1993-05-19 1994-09-27 General Dynamics Corporation Space Systems Division Multiple application paraboloid spacecraft structure
ATE164814T1 (en) * 1994-01-28 1998-04-15 Finmeccanica Spa STRUCTURAL ADAPTER FOR THE LOADING COMPARTMENT OF A LAUNCH ROCKET
RU2125526C1 (en) * 1995-11-16 1999-01-27 Ломанов Аполлон Анатольевич Lean-to for space station
US6416018B2 (en) * 1996-09-17 2002-07-09 The Boeing Company Satellite dispenser
US5984235A (en) * 1997-06-27 1999-11-16 Space Sciences Corporation Integrated launch and spacecraft propulsion system
US6193187B1 (en) * 1998-12-31 2001-02-27 Harry Scott Payload carry and launch system
US6286787B1 (en) * 1999-07-09 2001-09-11 Aero Astro, Inc. Small satellite GEO-to-LEO orbit transfer vehicle
US6543724B1 (en) * 1999-07-22 2003-04-08 Lockheed Martin Corporation Miniature satellite design
US6296206B1 (en) * 1999-12-01 2001-10-02 The Boeing Company Cantilever, bi-level platform satellite dispenser
US7070151B2 (en) * 2004-01-09 2006-07-04 Iostar Corporation In orbit space transportation and recovery system
US6565043B1 (en) * 2001-12-21 2003-05-20 The Boeing Company Redundant system for satellite inclination control with electric thrusters
NL1020271C2 (en) * 2002-03-28 2003-09-30 Dutch Space B V Spacecraft and method for assembling such a spacecraft, as well as adapter to be used in such a spacecraft.
US20050109878A1 (en) * 2002-03-28 2005-05-26 Dutch Space B.V. Spacecraft and method for building such a spacecraft and an adapter to be used in such a spacecraft
US8002219B2 (en) * 2006-11-17 2011-08-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Multi-functional annular fairing for coupling launch abort motor to space vehicle
US8016240B2 (en) * 2007-03-29 2011-09-13 The Boeing Company Satellites and satellite fleet implementation methods and apparatus
CN100475651C (en) * 2007-04-19 2009-04-08 上海交通大学 Awl-rod type butt and releasing gear for spacing micro-nano star station
FR2935686B1 (en) * 2008-09-08 2010-09-24 Snecma FAGOT HAVING TWO PAIRS OF RESERVOIRS AND AIRBORNE LAUNCHER COMPRISING SUCH A FAGOT
FR2945515B1 (en) * 2009-05-12 2012-06-01 Astrium Sas SYSTEM COMPRISING A MOTHER SPACE PROBE FORMING CARRIER SPACE VEHICLE AND A PLURALITY OF SPATIAL GIRL PROBES
CN201971170U (en) * 2010-11-25 2011-09-14 西北工业大学 Electromechanical integrated general butt joint device
US8789797B2 (en) * 2012-02-23 2014-07-29 Alliant Techsystems Inc. Payload adapters including antenna assemblies, satellite assemblies and related systems and methods

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2013041598A1 *

Also Published As

Publication number Publication date
US9963250B2 (en) 2018-05-08
FR2980177B1 (en) 2014-07-11
WO2013041598A1 (en) 2013-03-28
RU2566511C1 (en) 2015-10-27
EP2758310B1 (en) 2019-01-16
CN103930348A (en) 2014-07-16
IL231640A0 (en) 2014-05-28
CA2849338A1 (en) 2013-03-28
US20150001347A1 (en) 2015-01-01
CA2849338C (en) 2016-09-13
IL231640A (en) 2017-01-31
JP2014530144A (en) 2014-11-17
CN103930348B (en) 2016-08-24
FR2980177A1 (en) 2013-03-22

Similar Documents

Publication Publication Date Title
EP2758310B1 (en) Propulsion bay
US10717551B2 (en) Systems and methods for deploying a spacecraft arrangement
CA2380665C (en) Deployable radiator for a spacecraft
EP2810875B1 (en) Bi-modular propulsion system for orbit and attitude control of a satellite
EP2032437B1 (en) Method for placing in operational orbit an artificial satellite and associated propulsion device
EP2961656B1 (en) Space propulsion module having electric and solid-fuel chemical propulsion
EP2429900B1 (en) System comprising a mother space probe forming a carrier space vehicle and a plurality of daughter space probes
FR2990930A1 (en) PROPULSION SYSTEM FOR ORBIT CONTROL AND SATELLITE ATTITUDE CONTROL
FR2990193A1 (en) PROPULSION SYSTEM FOR ORBIT CONTROL AND SATELLITE ATTITUDE CONTROL
EP2878539B1 (en) System of nozzles and method for orbit and attitude control of a geostationary satellite
FR3004166A1 (en) SATELLITE SYSTEM COMPRISING TWO SATELLITES FIXED TO ONE ANOTHER AND METHOD FOR THEIR ORBIT
EP3765368B1 (en) System for placing a satellite in working orbit
WO2022112718A1 (en) Reusable space transportation system
EP3589550B1 (en) Method and device for the connection and linear separation of two elements stuck together
WO2009068475A1 (en) Device for reducing aerodynamic drag
EP2727844A2 (en) Optimised propulsion device for satellite attitude control and orbit control
FR3040693A1 (en) METHOD FOR LINKING AND LINEAR SEPARATING TWO ELEMENTS
FR3131281A1 (en) SYSTEM FOR BALANCING THE CENTER OF INERTIA OF A TELECOMMUNICATIONS SATELLITE.

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140328

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20180612

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20180808

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602012056013

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1089526

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190215

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190116

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1089526

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190516

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190416

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190417

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190516

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190416

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602012056013

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

26N No opposition filed

Effective date: 20191017

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190920

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190920

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20190930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20190920

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190920

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120920

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190116

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230911

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230816

Year of fee payment: 12

Ref country code: DE

Payment date: 20230818

Year of fee payment: 12